Propelling device for aeroplanes and the like



Feb. 6, 1923.

P. K. RUCKEL PROPELLING DEVICE FOR AEROPLANES AND THE LIKE Filed A r 8, 1921 2 sheet's-sheet 1 INVENTOR FIE-9'4 BY M6 ATTORNEY Feb. 6, 1923. 1,44%433 A P. K. RUCKEL PROPELLING DEVICE FOR AEROPLANES AND THE LIKE Filed Apr. 8, 1921 2 sheets-sheet 2 Patented Feb. b, 1923..

STATES Latte-t3 PHILLIP K. EUOKEL, OF SAGINAW, Ii IICHIGAN.

PROPELLING DEVICE FOR AEROPLANES Ann THE LIKE.

Application filed April 8, 1921. Serial No. 459,600.

To all whom it may concern:

Be it known that I, PHILLIP K. RUonnL, a citizen of the United States, residing at Saginaw, in the county of Saginaw and State of Michigan, have invented certain new and useful Improvements in Propelling Devices for Aeroplanes and the like; and I do hereby declare the following to be a full, clear, and exact description of the invention, such as will enable others skilled in the art to which it appertains to make and use the same.

This invention relates to propelling devices adapted for use on aeroplanes, dirigible balloons or any other devices in which the propelling power is obtained by the reaction of the air against propelling planes.

My improvement also may be applied as a means for obtaining power from air in motion, as for example, a wind engine, but my present application will for purposes of better illustration be limited to a descrip tion of the device as applied to an aeroplane.

The objects of my invention are, therefore, to provide in combination with an aeroplane or similar machine, a propelling device consisting of a plurality of pivotally mounted planes adapted to be revolved in a circular orbit, the pivotal axis of each plane being parallel with the common axis of revolution of all of the planes.

1 also provide means whereby each of the pivoted planes can be automatically tilted into various angular positions during its orbital revolution, so that the propelling; planes may be made to advance flat against the wind during partof their revolution and edgewise or feathering during the remainder of the revolution, and that part of the revolution during which they advance flatwise may be shifted to various parts of the circle oi? revolution by an adjusting cam device, whereby the function of the propelling planes can be quickly changed from that of propelling ahead, to lifting vertically or vice versa.

A further object of my invention is to arrange the tiltable propelling planes so that if the machine falls, thepropelling planes will occupy such positions as to offer the' maximum resistance to falling, somewhat after the manner of a parachute anchtherei'ore, check the falling speed.

With these and certain other objects in view which will appear later in the specificatlon, my invention comprises the devices described and claimed and the-equivalents thereof.

In the drawings, Fig. 1 is a top plan view of an aeroplane embodying my invention.

Fig. 2 is a front elevation, broken away in part, of the aeroplane shown in Fig. 1.

F ig. 3 is a diagrammatic top plan view. of the aeroplane of Fig. 1 with the propellin planes and fixed planes removed.

lis a side elevation of the aeroplane of Fig. .1, showing, diagrammatically, the propelling planes in lifting position.

Fig. 5 is a'similar elevation, partly broken away, showing, diagrammatically, the pro;- polling blades in their forward or driving position.

Fig. 6 is a fragmentary side view of one, of the wheels on which the propelling blades are pivotally mounted, the annular hub of the wheel being shown as rotatable around the lateral truss frame of the machine.

Fig. 7 is a part sectional side view on line Z of Fig. l, partly broken away, showing; the cam track that controls the tilting or feathering movement of the propelling. planes. the successive positions oi a propelling plane being indicated by dotted lines.

Fig. 8 is anenlarged sectional view taken on l ne 8-8 of Fig. 7, the view being broken away in part.

Figs. 9 and 10 are respectively a plan view and an edge view of one of the rollercarryingbars that co-a-ct'with the cam track to properly shift the radial positions of each of the feathering planes asthey revolve.

Fig. 11 is a diagrammatic top plan view of the driving connections between the motor and the annular hubs of the wheels upon which the propelling planes are mounted.

The aeroplane comprises the cockpit 2 and power plant 3 and a laterally extending truss frame l secured to'the top of the fuselag'e and extendin to the right or left thereof, as indicated in Figs. 1 and 3.

To the outer ends of the truss -frame l are preferably secured the usual fixed planes 5. 5, these planes being spaced apart from i the fuselage l to permit mounting, in the space between them, the propelling and liftmg mechanism to which my present 1nvention pertains. This propelling and lifting mechanism. comprises primarily a set or plurality of pivotally mounted planes adapted to be revolved about the central axis or the laterally extending truss frame 4, and means connected to each of said pivotally mounted planes whereby to automatically adjust or tilt the plane to successively changed radial positions curing the revolution of the plane about its central axis. Each plane of the set will expose its entire list surface to the resistance of the air curing a part or its revolution, and during the remainder of its travel or orbit will advance edge foremost, or approximately so, through the air, so as to leather and otter as little resistance as possible.

Preferably the sets of propelling planes, one at each side of the iusel. mounted as shown in Figs. 1, 2, 4 and 5, and this mounting will now be explained.

For each set of revolvable planes l pro vide a pair of wheels, 6 and 7, removably mounted on the truss frame 1-. Carried by the rims of the two wheels and pivotally mounted between them is the set oft planes, as 8 to 13 inclusive. When the wheels 6 and 7 are rotated, the planes 8 to 13 are revolved in circular orbit around the truss frame 4.

Referring to Fig. 6, showing a fragmentary view of one of the wheels, as 7, it will be seen that the rim 14 carries bearings 15 upon which the planes 8 to 13 are pivoted,

and spolr 16 connect the rim with an an nular hub 17, the interior of which forms an annular track, Fig. 8, that travels around frame 4, on sets of idler rolls 18 carried by the frame 4.

The plane-carrying wheels, 6 and 7, may be propelled in any suitable manner, but ll prefer to apply the power at the hubs 1'? of the wheels, as inoicated in Figs. 6 and 8, where 19 is a sprocket wheel carried by the hub 17. Upon the sprocket wheel is a drive chain 20, Fig. 5, which also encircles a sprocket 21, the horizontal location of which is indicated diagrammat-ically in Fig. 11. A second sprocket 22, carried by the shaft of sprocket 21, is connected by a chain 23 with a sprocket 24 mounted on a jack shaft 25. This shaft also carries a sprocket 26, which is connected by a drive chain 27 with the engine or other'source power 3, so that when the engine 3 is operated the jZtCli shaft 25 with its sprockets 26 and will transmit the driving power to the annular sprocket 19 through the s 22 and 21, thereby revolving the propelling planes bodily about the axis of the truss frame l.

For the purpose of lifting the plane yerlically, or nearly so. the downecoming plsu as, as 3 9, in 4-, should be ap proximately horizontal and the rip-going planes, 11 and 12, should be nearly vertinee-aces cal, while the backwardly moving planes, as 10 and the forwardly moving planes, 13 should be as nearly horizontal as is practicable.

I, therefore, provide means for radially tilting or positioning the revolving planes to automatically adjust them. to successively altered radial positions during their revolution about the central axis.

Any desired or suitable mechanism may be employed for this purpose, but I prefer, for purpose of illustration, to use the angular or radial adjusting devices shown in Figs. 7 to 10 inclusive.

Crosswise upon the end of the central shaft each tilt-able plane is secured a bar 29 having idler rolls 30 and 31 pivotally mounted at its ends.

Alongside one of the plane-supporting wheels, as 7, and spaced apart therefrom is a large circular cam 32 preferably built with spokes connected to an annular hub 34, this hub being mounted to rotate on idlers 35 carried by the truss frame 4, as indicated in Fig. 7.

This wheel 7 and the cam track 32 are shown in broken cross section in Fig. 8, with roller in place. The cam track comprises pan-telly closed channel around which the idler roller travels, as is shown diagrammatically by the dotted lines in Fig.7.

The cam 32 maybe rotated into various adjusted positions around the truss frame 4, the rota ion beil N eiliected by the pilot, by

means oil a pinion 36 carried by frame d and en acmean internal gear 37 mounted on line anniilar hub 3d of the cam. he pinion 36 may turned by a hand wheel 38 Within reach of the pilot and connected by any suitable usual arrangement or shafts and connections with the shaft of gear 36.

Referring now to Fig. 7, it will be seen that when the bar 2,9 of one of the propellii planes has one of its end rollers, as 31, t- .velir in the track 32, the radial or angu- 10.1' position of the bar 29, and consequently oi? the plane to which the bar is attached, will be determined by the relative position and or "it re 0% the 32 with respect to the or the propelling plane, it being remembered that the wheel and the cam are set in parallel planes slightly spaced apart, and that the arm and its rollers 31 and 30 form the operating connection between the tiltable planes und t-hc cam The shape and position of the cam 32 being such a o give the proper tilt to the "I i. u

other parts of their path of revolution. As indicated in Fig. 5, the planes that are driven rearwardly flat against the air, as 8 and 9-, can by turning cam 32, be made to advance fiatward in a downward direction, as shown in Fig. 4. 1n the position of the cam shown in Fig. 4, the planes 8 and 9 tend to lift the machine vertically, while in the position of the cam shown in Fig. 5 the planes 8 and 9 propel the machine forwardly. This shift of position is accomplished by the rotary adjustment of the cam 32 by means of the handwhee'l 88, or its equivalent. In order to produce the proper axial tilting or feathering action of the planes at any part of their orbit, it is only necessary to properly shift the cam 32, and this can be done while the planes are revolving.

It will be noticed by reference to Fig. 4 that the outer edge of one of the planes, as 9, is outside the boundary of the cam 32 and of the wheel 6, and the same is true with reference to positions of the planes indicated by numerals l and 1 but in the position of, say, plane 12, that edge of the plane which was outside the boundary of the wheel 6 is now within the boundary of the wheel and the opposite edge of the plane is outside the boundary.

To make this shift in the position of the plane while it revolves, I prefer to arrange the cam. track as shown in Fig. 7, where the rollers 80 and ill of arm 29 travel as indicated raniniatically by dotted lines. left-hand part of F 7, roller cling up along the cam and ther extremity of the cam, finally the cam groove at the end lt also be seen that roller 30, which at lower left-handposition shown in Fig. outside the boundary of cam 32, enters a other end of the cam groove 40, crosses first-mentioned end of the cam until it l .tes one revolution. Each of the ollers 30 and 31 makes a revolution alteriately inside the cam and then outside the am, thereby causing each of the planes 8 0 l3 to turn over on its axis 28 during sec nd half of each succeeding revolu- 11. ll ion cam has been shifted from tion shown in Fig. 1- to the position each of the propelling planes will *xactly same niann c as before, act to the car-n 32, but their worrj ljOSll'lOll with respect to. say, one bottom ot the fusel ge 1 will be shifted through apprrmiinately ninety degrees. When the can: 32 s in the position of the marhino will he lii'ed by the revolving planes, as and 9. and when the cam 32 in the ion shown in Fig. the plane will be driven ward by planes 8 9, and the su edina planes.

hen the plane is lifting. as in Fig. 4.

and as indicated diagrammatically at the right-hand side of Fig. 7, l have found it advisable to provide means for preventing the roller groove and thereby cramping the arm 29 which is carried by the shaft 28 and causing unnecessary :nic'tion. To avoid such accidental crowding of the roller 30, 1 fix to arm 99 a wiper or guide a l adapted to engage a fixed cam guide 42, which may be secured by means or spokes at?) to cam 32.

if the machine falls while the propelling planes are in the position shown in Fig. 5, that is, with planes 8 and 9 vertical, l1 and 12 horizontal and and 13 inclined inwardly at the top, it will be seen that each set or system of planesv will act after the manner .of a parachute to check the speed of falling and if the machine falls nose first with the planes 1 the position shown in Fig. 4, the same parachute eifect will be ob tained. 1f the machine falls in any other position will be possible for the operator by turning handwheel 38 and cam 32, to

quickly shift the of planes into such position that they will act effectively after the manner of a parachute to check the velocity of falling.

While l have shown and described my device as applied to an aeroplane having a it'uselage l and two or more fixed planes 5, it will be evident that my improved propelling mechanism may equally well be applied to various other uses as for example the propelling of dirigible air shipsand the like and that it may also be employed by mere reversal of its action as a wind wheel or ind mill to change wind energy into available mechanical energy.

Having thus described my invention, what claim and desire to secure by Letters Patout is:

l. Iln'an aeroplane including a fuselage and hired planes having a lifting, and propolling device comprising a set of planes, each plane pivotally supported at its ends, the planes of each set adapteu to be revolved about a central axis, means for so revolving said planes and positioning devices connected to each plane. said positioning devices comprising a radially projecting arm carried by eachplane. a roller on each end of said arm and a cam traclr of approximately circulai shape mounted in lined position and adapted to receive one end of said roller. the 9 ends of said cam traclr intersectingand 3 in inlet and outlet channels of suit. cam. whereby to eifect reversal said planes each circuit around said cam.

n an aeroplane including a fuselage, a late box truss projecting each side of the fuselage, a plurality of walls each havinn an. annular hub, idler rolls mounted at the corner of said true. .nd revolvably supporting said annular huh, and means for refrom lagging behind in the cam volvil'lg said hub arbund said truss substanporting suid ahfifliu hub, in internal gear earned by sald hub and a revolvable gear JtiaHy as described.

n'cludlng a fuselage, a meshl ng wlth szud internal gear and carrled 10 I 3. In an aeroplane i flate'ral b ox truss projecting at each side of by said truss. J 5 the fuselage, a plurality of Walls each hav- In testimony whereof, I aflix my signature;

ing an annular hub, idler rolls mounted at v V PHILLIP K. RUCKE'L.

the corners of said truss and revolvably sup- 

